JP2003176704A - Method for enhancing heat transfer inside turbulated cooling passage - Google Patents

Method for enhancing heat transfer inside turbulated cooling passage

Info

Publication number
JP2003176704A
JP2003176704A JP2002230695A JP2002230695A JP2003176704A JP 2003176704 A JP2003176704 A JP 2003176704A JP 2002230695 A JP2002230695 A JP 2002230695A JP 2002230695 A JP2002230695 A JP 2002230695A JP 2003176704 A JP2003176704 A JP 2003176704A
Authority
JP
Japan
Prior art keywords
gap
turbulator
cooling
electrode
passage
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
JP2002230695A
Other languages
Japanese (ja)
Other versions
JP4216540B2 (en
Inventor
Ching-Pang Lee
チン−パン・リー
Rong-Shi Paul Chiu
ロン−シ・ポール・チウ
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of JP2003176704A publication Critical patent/JP2003176704A/en
Application granted granted Critical
Publication of JP4216540B2 publication Critical patent/JP4216540B2/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
    • F28F13/00—Arrangements for modifying heat-transfer, e.g. increasing, decreasing
    • F28F13/06—Arrangements for modifying heat-transfer, e.g. increasing, decreasing by affecting the pattern of flow of the heat-exchange media
    • F28F13/12—Arrangements for modifying heat-transfer, e.g. increasing, decreasing by affecting the pattern of flow of the heat-exchange media by creating turbulence, e.g. by stirring, by increasing the force of circulation
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23H—WORKING OF METAL BY THE ACTION OF A HIGH CONCENTRATION OF ELECTRIC CURRENT ON A WORKPIECE USING AN ELECTRODE WHICH TAKES THE PLACE OF A TOOL; SUCH WORKING COMBINED WITH OTHER FORMS OF WORKING OF METAL
    • B23H9/00—Machining specially adapted for treating particular metal objects or for obtaining special effects or results on metal objects
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23H—WORKING OF METAL BY THE ACTION OF A HIGH CONCENTRATION OF ELECTRIC CURRENT ON A WORKPIECE USING AN ELECTRODE WHICH TAKES THE PLACE OF A TOOL; SUCH WORKING COMBINED WITH OTHER FORMS OF WORKING OF METAL
    • B23H9/00—Machining specially adapted for treating particular metal objects or for obtaining special effects or results on metal objects
    • B23H9/006—Cavity sinking
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23H—WORKING OF METAL BY THE ACTION OF A HIGH CONCENTRATION OF ELECTRIC CURRENT ON A WORKPIECE USING AN ELECTRODE WHICH TAKES THE PLACE OF A TOOL; SUCH WORKING COMBINED WITH OTHER FORMS OF WORKING OF METAL
    • B23H9/00—Machining specially adapted for treating particular metal objects or for obtaining special effects or results on metal objects
    • B23H9/10—Working turbine blades or nozzles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23H—WORKING OF METAL BY THE ACTION OF A HIGH CONCENTRATION OF ELECTRIC CURRENT ON A WORKPIECE USING AN ELECTRODE WHICH TAKES THE PLACE OF A TOOL; SUCH WORKING COMBINED WITH OTHER FORMS OF WORKING OF METAL
    • B23H9/00—Machining specially adapted for treating particular metal objects or for obtaining special effects or results on metal objects
    • B23H9/14—Making holes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
    • F28F1/00—Tubular elements; Assemblies of tubular elements
    • F28F1/10—Tubular elements and assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses
    • F28F1/40—Tubular elements and assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses the means being only inside the tubular element
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2212—Improvement of heat transfer by creating turbulence
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28D—HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT
    • F28D21/00—Heat-exchange apparatus not covered by any of the groups F28D1/00 - F28D20/00
    • F28D2021/0019—Other heat exchangers for particular applications; Heat exchange systems not otherwise provided for
    • F28D2021/0077—Other heat exchangers for particular applications; Heat exchange systems not otherwise provided for for tempering, e.g. with cooling or heating circuits for temperature control of elements
    • F28D2021/0078—Other heat exchangers for particular applications; Heat exchange systems not otherwise provided for for tempering, e.g. with cooling or heating circuits for temperature control of elements in the form of cooling walls

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • General Engineering & Computer Science (AREA)
  • Geometry (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Electrical Discharge Machining, Electrochemical Machining, And Combined Machining (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

<P>PROBLEM TO BE SOLVED: To enhance heat transfer and cooling efficiency in a cooling passage 10. <P>SOLUTION: This method for enhancing heat transfer and cooling efficiency in the cooling passage 10 includes forming a plurality of turbulator rings 14 in the passage, the rings projecting inwardly, substantially perpendicular to a cooling flow direction in the passage, and inward, and using a patterned electrode 16, forming at least one gap 22 in one or more of the turbulator rings, extending substantially parallel to the flow direction. <P>COPYRIGHT: (C)2003,JPO

Description

【発明の詳細な説明】Detailed Description of the Invention

【０００１】[0001]

【発明の属する技術分野】本発明は、ノズル又はバケッ
トのようなタービン構成部品内の冷却通路に関し、具体
的には、熱伝達を強化し従って冷却効率を強化するター
ビュレータ付き冷却通路に関する。FIELD OF THE INVENTION The present invention relates to cooling passages in turbine components such as nozzles or buckets, and more particularly to turbulated cooling passages for enhancing heat transfer and thus cooling efficiency.

【０００２】[0002]

【従来の技術】ガスタービン効率は、高温ガス通路に沿
って流れタービンブレードを駆動するタービンガスの温
度に正比例する。ガスタービンは、一般的に２７００°
Ｆにもなる運転温度を有する。これらの高温に耐えるた
めに、バケットは、最新の材料で製造され、一般的には
圧縮機の吐出空気である冷却媒体をバケットを通して流
すための平滑なボア冷却通路を一般に含む。通路はま
た、一般的に半径方向内側のバケット根元から半径方向
外側のバケット先端まで延びる。平滑なボア通路が今ま
で利用されてきたが、タービュレータなどの乱流促進装
置も、内部の熱伝達率を高めるために多くのガスタービ
ンバケットにおいては用いられている。熱伝達の強化
は、同じ冷却流量において平滑なボア通路と比べて２．
５倍もの高さになり得る。通常、タービュレータは、冷
却通路の内部表面に沿って内部突条又は粗面を含み、一
般的にセラミックコアを用いて冷却通路の内側に鋳造さ
れる。しかしながら、多くの現在用いられているタービ
ンにおいては、バケットの多くは、鋳造プロセスにより
形成された平滑な内部壁面を備える内部冷却通路を有し
ており、タービュレータを用いなければ冷却効果の強化
は得られない。多くの発電タービンバケットでは、成形
チューブ電解加工（ＳＴＥＭ）により穿孔された円形の
丸孔を用いて、タービン翼形部内側の半径方向の冷却流
れ通路を形成する。ＳＴＥＭは、導電材料中に３００：
１のような高いアスペクト比をもつ小径の深い孔を非接
触穿孔するのに用いられる。アスペクト比は、孔の最も
大きい横方向寸法、例えば直径に対する孔の長さ又は深
さの比であり、この孔の直径は、一部の特定の用途にお
いては、数ミリメートルほどまで小さい場合がある。Ｓ
ＴＥＭプロセスは、電極と被加工物の間にある空間内を
流れる電解質を通してそれらの間に電流を流すことを用
いて、電気溶解により材料を取り除く。Gas turbine efficiency is directly proportional to the temperature of the turbine gas flowing along a hot gas path and driving turbine blades. Gas turbines are typically 2700 °
It has an operating temperature of F. To withstand these high temperatures, buckets are typically made of modern materials and generally include smooth bore cooling passages for flowing a cooling medium, typically compressor discharge air, through the bucket. The passages also generally extend from a radially inner bucket root to a radially outer bucket tip. While smooth bore passages have been used to date, turbulence enhancers such as turbulators are also used in many gas turbine buckets to increase the internal heat transfer coefficient. Enhanced heat transfer compared to a smooth bore passage at the same cooling flow rate.
It can be as high as 5 times. Turbulators typically include internal ridges or rough surfaces along the inner surface of the cooling passages and are typically cast inside the cooling passages using a ceramic core. However, in many currently used turbines, many of the buckets have internal cooling passages with smooth internal wall surfaces formed by the casting process, and without a turbulator no enhanced cooling effect can be obtained. I can't. In many power turbine buckets, circular round holes drilled by molded tube electromachining (STEM) are used to form the radial cooling flow passages inside the turbine airfoils. STEM has 300:
Used for non-contact drilling of small diameter deep holes with high aspect ratio such as 1. Aspect ratio is the largest lateral dimension of a hole, for example the ratio of the length or depth of the hole to its diameter, which in some particular applications can be as small as a few millimeters. . S
The TEM process uses electrolysis to remove material by passing an electrical current between them through an electrolyte that flows in a space between the electrode and the work piece.

【０００３】[0003]

【発明が解決しようとする課題】冷却通路の内側の突条
すなわち環状のタービュレータ・リングは、’５７９出
願中に記載されているようにＳＴＥＭ穿孔プロセスの間
に形成することができる。これら円形のタービュレータ
・リングは、冷却流れ方向に垂直に通路中に突出して、
冷却通路の内側の熱伝達を強化するための乱渦流を生成
する。一般的に、ある期間現場で使用された後には、リ
ング間の表面には、冷却空気からのごみが蓄積して、望
ましくない絶縁層を形成し、従って冷却効率を低下させ
ることになる。ＳＴＥＭで穿孔されたタービュレータ付
き冷却通路の内側の熱伝達を更に強化し、同時にごみの
蓄積を減少させ、従って冷却効率を維持することができ
る改良された形状を有するのが望ましい。The ridges or annular turbulator rings inside the cooling passages can be formed during the STEM drilling process as described in the '579 application. These circular turbulator rings project into the passages perpendicular to the cooling flow direction,
It creates turbulent vortices to enhance heat transfer inside the cooling passages. Generally, after some field use, the surfaces between the rings will accumulate debris from the cooling air, forming an undesirable insulating layer and thus reducing cooling efficiency. It would be desirable to have an improved geometry that would further enhance heat transfer inside the STEM-perforated turbulated cooling passages while at the same time reducing debris accumulation and thus maintaining cooling efficiency.

【０００４】[0004]

【課題を解決するための手段】本発明の方法において、
既に形成されているタービュレータ・リングは、追加の
空気通路を提供しかつリング間の流れの淀み領域を防止
する軸方向に向いたギャップを備えるように改造され
る。In the method of the present invention,
Preformed turbulator rings are modified to have axially oriented gaps that provide additional air passage and prevent flow stagnation areas between the rings.

【０００５】ＳＴＥＭプロセスを用いてギャップを形成
するために、現存の半径方向の冷却通路より断面が僅か
に小さい電極が選択される。電極は、外部表面全体に絶
縁誘電材料すなわち被覆を有する。被覆の一部は、その
後、例えばレーザアブレーション技術を用いて除去され
て所望のギャップパターンを形成する。ギャップ間の軸
方向の間隔距離は、冷却通路内のタービュレータ・リン
グ間の間隔距離と等しい。周方向には、各リングに対し
て少なくとも２つのギャップが設けられる。ギャップ
は、隣接するリング間で整合されるか又はオフセットさ
れるかのいずれかにすることができる。次いで、パター
ン化された電極は、現存する冷却通路の内側に配置さ
れ、ＳＴＥＭプロセスを用いてタービュレータ・リング
内に多数の軸方向に向いたギャップが形成される。具体
的には、パターン化された電極は、電極と被加工物（バ
ケット）との間の電解液と電流の印加との組合せによ
り、タービュレータ・リングの隣接部分から金属を溶解
してリング中に軸方向のギャップを形成する。すでに上
述したように、これらのギャップは追加の空気通路を提
供することになるので、空気がギャップの端縁を通過す
るとき、追加の乱渦流が生成されて、表面の熱伝達を強
化し従って冷却効率を強化すると同時にごみの蓄積も減
少させることになる。In order to form the gap using the STEM process, electrodes with a cross section slightly smaller than the existing radial cooling passages are selected. The electrodes have an insulating dielectric material or coating over the outer surface. A portion of the coating is then removed using, for example, laser ablation techniques to form the desired gap pattern. The axial distance between the gaps is equal to the distance between the turbulator rings in the cooling passage. In the circumferential direction, at least two gaps are provided for each ring. The gaps can either be aligned or offset between adjacent rings. The patterned electrode is then placed inside an existing cooling passage and a number of axially oriented gaps are formed in the turbulator ring using the STEM process. Specifically, the patterned electrode combines the electrolyte and the application of an electric current between the electrode and the work piece (bucket) to melt the metal from the adjacent portion of the turbulator ring into the ring. Form an axial gap. As already mentioned above, these gaps will provide additional air passages so that as air passes through the edges of the gap, additional turbulent vortices will be created, enhancing the heat transfer on the surface and thus It will increase the cooling efficiency and at the same time reduce the accumulation of dust.

【０００６】従って、より広い形態において、本発明
は、冷却通路内の熱伝達及び冷却効率を強化する方法に
関し、該方法は、通路内の冷却流れ方向にほぼ垂直に、
内向きに突出する複数のタービュレータ・リングを該通
路内に形成する段階と、パターン化された電極を用い
て、タービュレータ・リングの１つ又はそれ以上の中
に、流れ方向に平行に延びる少なくとも１つのギャップ
を形成する段階とを含む。Accordingly, in a broader aspect, the present invention relates to a method of enhancing heat transfer and cooling efficiency in a cooling passage, the method being generally perpendicular to the cooling flow direction in the passage.
Forming a plurality of inwardly projecting turbulator rings within the passageway and using patterned electrodes to extend at least one of the turbulator rings parallel to the flow direction. Forming two gaps.

【０００７】別の形態において、本発明は、被加工物内
の冷却通路の内側の半径方向内向きに突出するタービュ
レータ・リング中にギャップを形成するための方法に関
し、該方法は、（ａ）その上に電気絶縁材料を具えてお
り、該電気絶縁材料が、非絶縁部分により中断され、従
ってタービュレータ・リング内の意図したギャップの位
置にほぼ向かい合って、その外側表面の周りに非絶縁部
分のパターンを生じる電極を前記通路の内部に配置する
段階と、（ｂ）冷却通路を通して電極と冷却通路の内部
表面との間に電解液を流す段階と、電極と被加工物との
間に電流を流して、タービュレータ・リング中にギャッ
プを形成する段階とを含む。In another aspect, the invention relates to a method for forming a gap in a radially inwardly projecting turbulator ring inside a cooling passage in a workpiece, the method comprising: (a) An electrically insulative material is provided thereon, the electrically insulative material being interrupted by the non-insulating portion and thus substantially facing the intended location of the gap in the turbulator ring and surrounding the outer surface of the non-insulating portion. Placing a patterned electrode inside the passage, (b) flowing an electrolyte through the cooling passage between the electrode and the inner surface of the cooling passage, and applying an electric current between the electrode and the workpiece. Flowing to form a gap in the turbulator ring.

【０００８】[0008]

【発明の実施の形態】図１を参照すると、機械構成部品
１２（例えば、高圧タービンノズル又はバケット）内の
冷却通路１０は、一般的にバケット（又は他の構成部
品）が鋳造されるときに、平滑なボアとして形成され
る。その後、通路は、該通路のほぼ全長に沿って軸方向
に間隔を置いて配置された状態になった複数の環状の突
条すなわちタービュレータ・リング１４を含むように成
形し直される。タービュレータ・リング１４は、ＳＴＥ
Ｍ穿孔プロセスの間にパターン化された電極によって形
成されることができ、このパターン化された電極は、環
状の溝を、該環状の溝の間にタービュレータ・リングを
後に残して通路内に形成する。言い換えれば、最初の通
路直径は、タービュレータ・リングの内径とほぼ同一で
ある。’５７９出願においては、タービュレータ・リン
グ及びギャップは、単一の工程で形成される。本発明で
は、ＳＴＥＭ穿孔を利用して、リング中にギャップがな
い現存のタービュレータ付き通路に対して「改造」を施
すことができる強化を行う。DETAILED DESCRIPTION OF THE INVENTION Referring to FIG. 1, a cooling passage 10 in a machine component 12 (eg, a high pressure turbine nozzle or bucket) is typically used when the bucket (or other component) is being cast. , Formed as a smooth bore. The passage is then reshaped to include a plurality of annular ridges or turbulator rings 14 that are axially spaced along substantially the entire length of the passage. Turbulator ring 14 is STE
M may be formed by a patterned electrode during the perforation process, the patterned electrode forming an annular groove in the passageway leaving behind a turbulator ring between the annular grooves. To do. In other words, the initial passage diameter is approximately the same as the inner diameter of the turbulator ring. In the '579 application, the turbulator ring and gap are formed in a single step. The present invention utilizes STEM drilling to provide enhancements that allow "remodeling" of existing turbulated passages that have no gaps in the ring.

【０００９】図２は、予め形成されたタービュレータ・
リング１４中に軸方向に向けられかつ周方向に配列され
たギャップを形成するように設計された電極１６を示
す。具体的には、電極１６は、通路１０の直径より僅か
に小さく、また、特にタービュレータ・リング１４の内
径よりも小さい外径を有する中空で円筒形の管である。
この例示的な実施形態において、電極の内径は、タービ
ュレータ・リング１４の内径より約０．００５インチ小
さい。電極１６は、ほぼその全長にわたって誘電体、す
なわち電気絶縁被覆１８を施される。被覆１８の一部
は、例えば、レーザアブレーション法により選択的に除
去されて、図２に示すような所望のギャップパターンを
形成する。電極の今露出された（すなわち、非絶縁の）
部分２０の形状、寸法及び軸方向の間隔距離は、タービ
ュレータ・リング１４中の所望のギャップ２２に対応す
る。具体的には、非絶縁ギャップ部分は、電極１６とタ
ービュレータ・リングとの間を流れる電解液と、電極と
バケットとの間の電流の印加と協働して、電極の露出し
た部分２０に近接するタービュレータ・リング１４から
金属材料を取り除き、その結果ギャップ２２（図４を参
照）を形成する。周方向には、タービュレータ・リング
１４毎に少なくとも１つ、好ましくは２つのギャップ２
２を有することが好ましく、またギャップ２２は隣接す
るタービュレータ間で整合されていても又はオフセット
されていてもよい。FIG. 2 shows a preformed turbulator.
Shown are electrodes 16 designed to form axially oriented and circumferentially aligned gaps in ring 14. Specifically, the electrode 16 is a hollow, cylindrical tube having a diameter slightly smaller than the diameter of the passage 10 and, in particular, an outer diameter smaller than the inner diameter of the turbulator ring 14.
In this exemplary embodiment, the inner diameter of the electrode is about 0.005 inch less than the inner diameter of turbulator ring 14. The electrode 16 is provided with a dielectric or electrically insulating coating 18 over substantially its entire length. A portion of the coating 18 is selectively removed by, for example, laser ablation to form the desired gap pattern as shown in FIG. Electrodes now exposed (ie, non-insulated)
The shape, dimensions, and axial spacing of the portions 20 correspond to the desired gap 22 in the turbulator ring 14. Specifically, the non-insulating gap portion is proximate to the exposed portion 20 of the electrode in cooperation with the electrolyte flowing between the electrode 16 and the turbulator ring and the application of current between the electrode and the bucket. The metallic material is removed from the turbulator ring 14 which results in the formation of the gap 22 (see FIG. 4). In the circumferential direction, at least one, preferably two gaps 2 per turbulator ring 14 are provided.
2 is preferred and the gap 22 may be aligned or offset between adjacent turbulators.

【００１０】ギャップ２２は、追加の空気通路を提供
し、タービュレータ間に流れの淀み領域が形成されるの
を防止する。空気がギャップ２２を通過すると、追加の
乱渦流が生成されて表面の熱伝達を強化することにな
る。ギャップ２２はまた、タービュレータ・リング間の
ごみの蓄積を減少させ、それによって冷却効率を維持す
る。The gap 22 provides additional air passage and prevents the formation of flow stagnation regions between the turbulators. As air passes through the gap 22, additional turbulent vortices will be created to enhance surface heat transfer. The gap 22 also reduces debris build-up between the turbulator rings, thereby maintaining cooling efficiency.

【００１１】本発明を、現在最も実用的で好ましい実施
形態であると考えられるものに関して説明してきたが、
本発明は、開示した実施形態に限定されるべきではな
く、反対に、特許請求の範囲の技術思想及び技術的範囲
に含まれる様々な変更及び均等な構成を保護しようとす
るものであることを理解されたい。While this invention has been described in what is presently considered to be the most practical and preferred embodiments,
The present invention should not be limited to the disclosed embodiments, but on the contrary, aims to protect various modifications and equivalent configurations included in the technical idea and the technical scope of the claims. I want you to understand.

【００１２】特許請求の範囲に示す参照符号は、本発明
の技術的範囲を狭めることを意図するものではなく、そ
れらを容易に理解することを意図するものである。Reference signs in the claims are not intended to narrow the scope of the invention, but to facilitate their understanding.

【図面の簡単な説明】[Brief description of drawings]

【図１】 従来のタービュレータ付き冷却通路の断面
図。FIG. 1 is a sectional view of a conventional cooling passage with a turbulator.

【図２】 本発明によるパターン化された電極の概略側
面図。2 is a schematic side view of a patterned electrode according to the present invention. FIG.

【図３】 図１に類似しているが、図２の電極がその中
に挿入されている断面図。3 is a cross-sectional view similar to FIG. 1 but with the electrodes of FIG. 2 inserted therein.

【図４】 本発明による熱伝達強化用のギャップを有す
る、タービュレータ付き冷却通路の一部の斜視図。FIG. 4 is a perspective view of a portion of a cooling passage with a turbulator having a gap for enhancing heat transfer according to the present invention.

【符号の説明】[Explanation of symbols]

１０ 冷却通路 １２ 被加工物 １４ タービュレータ・リング ２２ ギャップ 10 cooling passages 12 Workpiece 14 Turbulator Ring 22 gap

─────────────────────────────────────────────────────
─────────────────────────────────────────────────── ───

【手続補正書】[Procedure amendment]

【提出日】平成１４年１０月７日（２００２．１０．
７）[Submission date] October 7, 2002 (2002.10.
7)

【手続補正１】[Procedure Amendment 1]

【補正対象書類名】明細書[Document name to be amended] Statement

【補正対象項目名】特許請求の範囲[Name of item to be amended] Claims

【補正方法】変更[Correction method] Change

【補正内容】[Correction content]

【特許請求の範囲】[Claims]

【手続補正２】[Procedure Amendment 2]

【補正対象書類名】明細書[Document name to be amended] Statement

【補正対象項目名】０００９[Correction target item name] 0009

【補正方法】変更[Correction method] Change

【補正内容】[Correction content]

【０００９】図２は、予め形成されたタービュレータ・
リング１４中に軸方向に向けられかつ周方向に配列され
たギャップを形成するように設計された電極１６を示
す。具体的には、電極１６は、通路１０の直径より僅か
に小さく、また、特にタービュレータ・リング１４の内
径よりも小さい外径を有する中空で円筒形の管である。
この例示的な実施形態において、電極の外径は、タービ
ュレータ・リング１４の内径より約０．００５インチ小
さい。電極１６は、ほぼその全長にわたって誘電体、す
なわち電気絶縁被覆１８を施される。被覆１８の一部
は、例えば、レーザアブレーション法により選択的に除
去されて、図２に示すような所望のギャップパターンを
形成する。電極の今露出された（すなわち、非絶縁の）
部分２０の形状、寸法及び軸方向の間隔距離は、タービ
ュレータ・リング１４中の所望のギャップ２２に対応す
る。具体的には、非絶縁ギャップ部分は、電極１６とタ
ービュレータ・リングとの間を流れる電解液と、電極と
バケットとの間の電流の印加と協働して、電極の露出し
た部分２０に近接するタービュレータ・リング１４から
金属材料を取り除き、その結果ギャップ２２（図４を参
照）を形成する。周方向には、タービュレータ・リング
１４毎に少なくとも１つ、好ましくは２つのギャップ２
２を有することが好ましく、またギャップ２２は隣接す
るタービュレータ間で整合されていても又はオフセット
されていてもよい。FIG. 2 shows a preformed turbulator.
Shown are electrodes 16 designed to form axially oriented and circumferentially aligned gaps in ring 14. Specifically, the electrode 16 is a hollow, cylindrical tube having a diameter slightly smaller than the diameter of the passage 10 and, in particular, an outer diameter smaller than the inner diameter of the turbulator ring 14.
In this exemplary embodiment, the outer diameter of the electrode is about 0.005 inches smaller than the inner diameter of turbulator ring 14. The electrode 16 is provided with a dielectric or electrically insulating coating 18 over substantially its entire length. A portion of the coating 18 is selectively removed by, for example, laser ablation to form the desired gap pattern as shown in FIG. Electrodes now exposed (ie, non-insulated)
The shape, dimensions, and axial spacing of the portions 20 correspond to the desired gap 22 in the turbulator ring 14. Specifically, the non-insulating gap portion is proximate to the exposed portion 20 of the electrode in cooperation with the electrolyte flowing between the electrode 16 and the turbulator ring and the application of current between the electrode and the bucket. The metallic material is removed from the turbulator ring 14 which results in the formation of the gap 22 (see FIG. 4). In the circumferential direction, at least one, preferably two gaps 2 per turbulator ring 14 are provided.
2 is preferred and the gap 22 may be aligned or offset between adjacent turbulators.

───────────────────────────────────────────────────── フロントページの続き (72)発明者 ロン−シ・ポール・チウ アメリカ合衆国、ニューヨーク州、グレン モント、フィールズ・エンド・ドライブ、 81番 Ｆターム(参考） 3C059 AA02 AB01 GB05 3G002 CA07 CA15 CB05 GA08 GB01   ─────────────────────────────────────────────────── ─── Continued front page    (72) Inventor Ron-si Paul Chiu             Glenn, New York, United States             Mont, Fields End Drive,             81 F-term (reference) 3C059 AA02 AB01 GB05                 3G002 CA07 CA15 CB05 GA08 GB01

Claims (10)

【特許請求の範囲】[Claims] 【請求項１】 冷却通路（１０）内の熱伝達及び冷却効
率を強化する方法であって、 該通路内の冷却流れ方向にほぼ垂直に、内向きに突出す
る複数のタービュレータ・リング（１４）を該通路内に
形成する段階と、 パターン化された電極（１６）を用いて、前記タービュ
レータ・リングの１つ又はそれ以上の中に、前記流れ方
向に平行に延びる少なくとも１つのギャップ（２２）を
形成する段階と、を含むことを特徴とする方法。1. A method for enhancing heat transfer and cooling efficiency within a cooling passage (10), the plurality of turbulator rings (14) projecting inwardly substantially perpendicular to the direction of cooling flow within the passage. At least one gap (22) extending parallel to the flow direction in one or more of the turbulator rings using a patterned electrode (16). Forming a. 【請求項２】 前記少なくとも１つのギャップ（２２）
は、２つ又はそれ以上の該ギャップを含むことを特徴と
する、請求項１に記載の方法。2. The at least one gap (22)
The method according to claim 1, characterized in that comprises two or more of said gaps. 【請求項３】 前記少なくとも１つのギャップ（２２）
は、前記複数のタービュレータ・リング（１４）の各々
の中に形成されることを特徴とする、請求項１に記載の
方法。3. The at least one gap (22)
A method according to claim 1, characterized in that is formed in each of the plurality of turbulator rings (14). 【請求項４】 前記タービュレータ・リング（１４）及
び前記ギャップ（２２）は、電解加工により形成される
ことを特徴とする、請求項１に記載の方法。4. Method according to claim 1, characterized in that the turbulator ring (14) and the gap (22) are formed by electrolytic machining. 【請求項５】 被加工物（１２）内の冷却通路（１０）
の内側の半径方向内向きに突出するタービュレータ・リ
ング中にギャップ（２２）を形成するための方法であっ
て、 その上に電気絶縁材料（１８）を具えており、該電気絶
縁材料が、非絶縁部分（２０）により中断され、従って
前記タービュレータ・リング内の意図したギャップの位
置にほぼ向かい合って、その外側表面の周りに非絶縁部
分（２０）のパターンを生じる電極（１６）を前記通路
（１０）の内部に配置する段階と、 前記冷却通路を通して前記電極と前記冷却通路の内部表
面との間に電解液を流す段階と、 前記電極と前記被加工物との間に電流を流して、前記タ
ービュレータ・リング（１４）中に前記ギャップ（２
２）を形成する段階と、を含むことを特徴とする方法。5. A cooling passage (10) in a workpiece (12).
A method for forming a gap (22) in a radially inwardly projecting turbulator ring on the inside of, comprising an electrically insulative material (18) thereon, the electrically insulative material comprising: The electrode (16) interrupted by the insulating portion (20) and thus approximately facing the intended position of the gap in the turbulator ring, resulting in a pattern of non-insulating portions (20) around its outer surface, the electrode (16). 10) placing inside, flowing an electrolyte through the cooling passage between the electrode and the inner surface of the cooling passage, and passing an electric current between the electrode and the workpiece, The gap (2) in the turbulator ring (14)
2) forming step 2). 【請求項６】 前記少なくとも１つのギャップ（２２）
は、２つ又はそれ以上の該ギャップを含むことを特徴と
する、請求項５に記載の方法。6. The at least one gap (22)
The method according to claim 5, characterized in that comprises two or more of said gaps. 【請求項７】 前記少なくとも１つのギャップ（２２）
は、前記複数のタービュレータ・リング（１４）の各々
の中に形成されることを特徴とする、請求項５に記載の
方法。7. The at least one gap (22)
The method of claim 5, wherein is formed in each of the plurality of turbulator rings (14). 【請求項８】 前記タービュレータ・リング（１４）及
び前記ギャップ（２２）は、電解加工により形成される
ことを特徴とする、請求項５に記載の方法。8. A method according to claim 5, characterized in that the turbulator ring (14) and the gap (22) are formed by electrolytic machining. 【請求項９】 前記冷却通路（１０）は、ガスタービン
ノズル構成部品（１２）内に設けられていることを特徴
とする、請求項５に記載の方法。9. Method according to claim 5, characterized in that the cooling passages (10) are provided in a gas turbine nozzle component (12). 【請求項１０】 前記冷却通路（１０）は、ガスタービ
ンバケット構成部品（１２）内に設けられていることを
特徴とする、請求項５に記載の方法。10. Method according to claim 5, characterized in that the cooling passages (10) are provided in a gas turbine bucket component (12).
JP2002230695A 2001-08-09 2002-08-08 Method for enhancing heat transfer inside a cooling passage with a turbulator Expired - Fee Related JP4216540B2 (en)

Applications Claiming Priority (2)

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US09/925,024 US6582584B2 (en) 1999-08-16 2001-08-09 Method for enhancing heat transfer inside a turbulated cooling passage
US09/925024 2001-08-09

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